EP2014978A1 - Utilisation de gaz inertes destinés à isoler l'oxydant du combustible - Google Patents

Utilisation de gaz inertes destinés à isoler l'oxydant du combustible Download PDF

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Publication number
EP2014978A1
EP2014978A1 EP07013518A EP07013518A EP2014978A1 EP 2014978 A1 EP2014978 A1 EP 2014978A1 EP 07013518 A EP07013518 A EP 07013518A EP 07013518 A EP07013518 A EP 07013518A EP 2014978 A1 EP2014978 A1 EP 2014978A1
Authority
EP
European Patent Office
Prior art keywords
fuel
inert gas
inlet opening
fuel nozzle
burner
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP07013518A
Other languages
German (de)
English (en)
Inventor
Malte Dr. Blomeyer
Olga Deiss
Andre Kluge
Thomas Kunadt
Berthold Köstlin
Martin Lenze
Paul Pixner
Uwe Sieber
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Siemens AG
Original Assignee
Siemens AG
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Siemens AG filed Critical Siemens AG
Priority to EP07013518A priority Critical patent/EP2014978A1/fr
Priority to PCT/EP2008/058544 priority patent/WO2009007293A1/fr
Priority to EP08761415A priority patent/EP2162678A1/fr
Priority to CN200880101383A priority patent/CN101772674A/zh
Priority to US12/665,970 priority patent/US20100186417A1/en
Publication of EP2014978A1 publication Critical patent/EP2014978A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/46—Details, e.g. noise reduction means
    • F23D14/72—Safety devices, e.g. operative in case of failure of gas supply
    • F23D14/78—Cooling burner parts
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/283—Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23C—METHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  A CARRIER GAS OR AIR 
    • F23C2900/00—Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
    • F23C2900/07022—Delaying secondary air introduction into the flame by using a shield or gas curtain
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2214/00—Cooling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23L—SUPPLYING AIR OR NON-COMBUSTIBLE LIQUIDS OR GASES TO COMBUSTION APPARATUS IN GENERAL ; VALVES OR DAMPERS SPECIALLY ADAPTED FOR CONTROLLING AIR SUPPLY OR DRAUGHT IN COMBUSTION APPARATUS; INDUCING DRAUGHT IN COMBUSTION APPARATUS; TOPS FOR CHIMNEYS OR VENTILATING SHAFTS; TERMINALS FOR FLUES
    • F23L2900/00—Special arrangements for supplying or treating air or oxidant for combustion; Injecting inert gas, water or steam into the combustion chamber
    • F23L2900/07002—Injecting inert gas, other than steam or evaporated water, into the combustion chambers

Definitions

  • the present invention relates to the protection of a burner from excessive heating in the combustion of a fuel.
  • a common method of cooling is the coating of the affected component surfaces with a cooling air film.
  • Another possibility is the coating of the component surface with special ceramics. Since a defined fuel-air mixture is required for the combustion, and swirl blades are sometimes used to evenly mix the fuel with the air and thus to avoid temperature peaks during combustion.
  • the inventive method for protecting a burner from excessive heating during combustion of a fuel in a combustion chamber is characterized in that the fuel is injected through a fuel nozzle and at the same time an inert gas in the vicinity of the injected fuel are injected into the combustion chamber, that until the production of an ignitable mixture, the fuel is spatially separated from an oxidizer by the inert gas.
  • the fuel and the inert gas are thus simultaneously injected into the combustion chamber.
  • the inert gas surrounds the fuel so that the inert gas forms a protective layer shielding the fuel.
  • the fuel does not come so in the immediate vicinity of the burner in contact with a gas in the combustion chamber, which may contain oxygen as an oxidizer. In this way, near the burner does not form an ignitable mixture of fuel and an oxidizer.
  • Inert gases are gases that are very slow to react, meaning that they only participate in a few chemical reactions.
  • the inert gases include, for example, nitrogen, water vapor, carbon dioxide, and all noble gases.
  • the inert gas used in the present invention may be, for example, nitrogen, carbon dioxide, a noble gas, ie helium, argon, neon, krypton, radon, xenon, or a mixture of these.
  • the inventive spatial shielding of the fuel by the inert gas from an oxidizer makes it possible to use hydrogen as fuel.
  • suitable fuels for example, crude oil, natural gas or synthesis gas, may also be used as fuels instead of hydrogen.
  • the inert gas used can preferably be injected into the combustion chamber through an inlet opening annularly surrounding the fuel inlet opening of the fuel nozzle, so that the fuel stream is completely enclosed by an inert gas envelope. It is advantageous if the inert gas inlet opening is as close as possible to the fuel nozzle.
  • the oxidizer used can additionally be spatially injected from the fuel nozzle into the combustion chamber. In this way, the location of the ignition can be controlled and influenced. It can thereby control both the flame, as well as the spatial position of the mixing zone.
  • the present method can be used in particular in the context of the operation of a gas turbine.
  • the fuel nozzle according to the invention comprises at least one fuel inlet opening, which is surrounded by an inert gas inlet opening, which allows a spatial separation of the fuel from an oxidizer by injecting an inert gas.
  • the fuel inlet opening can be completely surrounded by the inert gas inlet opening, for example, annularly. Furthermore, the fuel inlet opening may be surrounded concentrically by the inert gas inlet opening.
  • the inert gas inlet opening may also consist of a plurality of individual openings arranged around the fuel inlet opening.
  • the advantage of the fuel nozzle according to the invention is that fuel and oxidizer are initially spatially separated from each other, whereby the combustion can be controlled.
  • a burner according to the invention comprises at least one fuel nozzle according to the invention.
  • a gas turbine according to the invention is equipped with at least one burner according to the invention.
  • FIG. 1 shows a section through a fuel nozzle according to the invention in the longitudinal direction.
  • FIG. 2 shows a cross section through a fuel nozzle according to the invention.
  • FIG. 3 shows a cross section through an alternative fuel nozzle according to the invention.
  • FIG. 1 shows a section along the longitudinal axis 11 through a fuel nozzle according to the invention.
  • the fuel nozzle may for example be part of a combustion chamber of a gas turbine.
  • the fuel nozzle 1 has a housing 2 in which a fuel inlet opening 3 and an inert gas inlet opening 4 are located.
  • the fuel inlet 3 is parallel to the longitudinal axis 11 in the middle of the burner nozzle 1 is arranged.
  • the inert gas inlet opening 4 is located farther from the longitudinal axis 11 than the fuel inlet opening 3. It likewise extends parallel to the longitudinal axis 11 and surrounds the fuel inlet opening 3 concentrically.
  • the inert gas inlet opening 4 and the fuel inlet opening 3 are separated from one another by a part of the housing 2.
  • the fuel nozzle 1 is located in a combustion chamber into which air 7 is introduced as an oxidizing agent.
  • Fuel 5 is now injected into the combustion chamber through the fuel inlet opening 3.
  • the flow direction of the fuel 5 is indicated by arrows 9.
  • an inert gas 6 is injected into the combustion chamber through the inert gas inlet opening 4 in such a way that the inert gas 6 shields the fuel 5 from the air 7 located in the combustion chamber.
  • the flow direction of the inert gas is indicated by arrows 8.
  • the inert gas used may be, for example, nitrogen, carbon dioxide, a noble gas or a mixture of these substances.
  • the fuel used may include, but not be limited to, petroleum, natural gas, but also hydrogen. There is also the possibility that the fuel already an oxidizing agent, for example. Air, is mixed in an amount that can not lead to ignition.
  • the FIG. 2 shows the related FIG. 1 described fuel nozzle 1 in a cross section perpendicular to the longitudinal axis 11. It can be seen in FIG. 2
  • the fuel inlet 3 has a circular cross section and is located in the middle of the fuel nozzle 1.
  • the cross section of the fuel inlet 3 may alternatively have any other shape.
  • the inert gas inlet 4 is arranged annularly around the fuel inlet 3. Through the fuel inlet 3, fuel 5 can be injected into the combustion chamber. Through the Inertgaseinlassö réelle 4, an inert gas, as in connection with FIG. 1 described be injected into the combustion chamber.
  • FIG. 3 a second embodiment based on the FIGS. 1 and 3 described in more detail.
  • the elements off FIG. 3 which correspond to elements which have already been described in connection with the first embodiment, are given the same reference numerals and will not be described again.
  • FIG. 3 shows the cross section perpendicular to the longitudinal axis 11 of the fuel nozzle 1.
  • the housing 2 of the fuel nozzle 1 which comprises a centrally arranged fuel inlet opening 3 and annularly arranged around the fuel inlet opening 3 Inertgaseinlassötechnisch 10.
  • the fuel inlet 3 again has a circular cross-section.
  • the cross section may also have any other shape.
  • individual inert gas inlet openings 10 each have a circular cross-section. They are annular, arranged concentrically around the fuel inlet opening 3. Also, the inert gas inlet openings 10 may be alternative to the in FIG. 3 shown circular cross section have any other shape of the cross section.
  • the operation of the fuel nozzle described in this embodiment corresponds to the fuel nozzle described in the first embodiment.
  • the inert gas discharge port completely surrounds the fuel discharge port in the present embodiment, or the inert gas discharge ports are evenly distributed around the fuel discharge port, it is basically also possible that the inert gas discharge port only partially surrounds the fuel discharge port or the inert gas discharge ports are unevenly distributed around the fuel discharge port. This modification is particularly appropriate if the oxidizing agent is distributed unevenly in the combustion chamber.
  • the present invention is characterized overall in that it provides effective protection of the burner from excessive temperatures while allowing control of the spatial location of the ignition and the flame.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
EP07013518A 2007-07-10 2007-07-10 Utilisation de gaz inertes destinés à isoler l'oxydant du combustible Withdrawn EP2014978A1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
EP07013518A EP2014978A1 (fr) 2007-07-10 2007-07-10 Utilisation de gaz inertes destinés à isoler l'oxydant du combustible
PCT/EP2008/058544 WO2009007293A1 (fr) 2007-07-10 2008-07-03 Utilisation de gaz inertes pour faire écran à un oxydant et à un combustible
EP08761415A EP2162678A1 (fr) 2007-07-10 2008-07-03 Utilisation de gaz inertes pour faire écran à un oxydant et à un combustible
CN200880101383A CN101772674A (zh) 2007-07-10 2008-07-03 使用惰性气体隔离氧化剂与燃料
US12/665,970 US20100186417A1 (en) 2007-07-10 2008-07-03 Use of inert gases for shielding oxidizer and fuel

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP07013518A EP2014978A1 (fr) 2007-07-10 2007-07-10 Utilisation de gaz inertes destinés à isoler l'oxydant du combustible

Publications (1)

Publication Number Publication Date
EP2014978A1 true EP2014978A1 (fr) 2009-01-14

Family

ID=38941824

Family Applications (2)

Application Number Title Priority Date Filing Date
EP07013518A Withdrawn EP2014978A1 (fr) 2007-07-10 2007-07-10 Utilisation de gaz inertes destinés à isoler l'oxydant du combustible
EP08761415A Withdrawn EP2162678A1 (fr) 2007-07-10 2008-07-03 Utilisation de gaz inertes pour faire écran à un oxydant et à un combustible

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP08761415A Withdrawn EP2162678A1 (fr) 2007-07-10 2008-07-03 Utilisation de gaz inertes pour faire écran à un oxydant et à un combustible

Country Status (4)

Country Link
US (1) US20100186417A1 (fr)
EP (2) EP2014978A1 (fr)
CN (1) CN101772674A (fr)
WO (1) WO2009007293A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2520857A1 (fr) * 2011-05-05 2012-11-07 General Electric Company Buse de chambre de combustion et procédé pour fournir du carburant à une chambre de combustion
EP2653698A1 (fr) * 2012-04-19 2013-10-23 Linde Aktiengesellschaft Procédé de fonctionnement d'une unité de turbine à gaz

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR101371291B1 (ko) * 2012-05-04 2014-03-07 고등기술연구원연구조합 비 용융 및 부분 용융형 분류층 가스화기
DE102012216267A1 (de) * 2012-09-13 2014-03-13 Siemens Aktiengesellschaft Messvorrichtungsgehäuse
DE102012216508A1 (de) * 2012-09-17 2014-03-20 Siemens Aktiengesellschaft Vergasungsbrenner mit Inertgasschleier zwischen Brennstaubkanal und Oxidationsmittelkanal
DE102012216557A1 (de) * 2012-09-17 2014-03-20 Siemens Aktiengesellschaft Brenner, insbesondere Vergasungsbrenner, mit transpirativ wirkender Bauteilkühlung
DE102012216505A1 (de) * 2012-09-17 2014-03-20 Siemens Aktiengesellschaft Vergasungsbrenner mit Inertgasschleier zwischen Pilotbrenner und Staubbrenner
US9562692B2 (en) 2013-02-06 2017-02-07 Siemens Aktiengesellschaft Nozzle with multi-tube fuel passageway for gas turbine engines
CN104019447B (zh) * 2013-03-01 2016-02-03 西安航天远征流体控制股份有限公司 开工烧嘴点火器氮气保护装置
CN112050253B (zh) * 2020-09-18 2022-04-22 中国航发四川燃气涡轮研究院 一种多重隔热燃油喷嘴
US11306661B1 (en) * 2020-12-04 2022-04-19 General Electric Company Methods and apparatus to operate a gas turbine engine with hydrogen gas
US20220373182A1 (en) * 2021-05-21 2022-11-24 General Electric Company Pilot fuel nozzle assembly with vented venturi
US20240288159A1 (en) * 2023-02-23 2024-08-29 Raytheon Technologies Corporation Turbine engine fuel injector assembly with annular fuel outlet
US12038177B1 (en) * 2023-03-14 2024-07-16 Rtx Corporation Fuel injector assembly for gas turbine engine with fuel, air and steam injection

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0375311A1 (fr) * 1988-12-22 1990-06-27 General Electric Company Couvercle incorporé de buse à carburant pour chambre de combustion d'une turbine à gaz
EP0473906A1 (fr) * 1990-08-01 1992-03-11 Corning Incorporated Ensemble de brûleur d'oxygène-combustible et le régime
EP0718554A2 (fr) * 1994-12-20 1996-06-26 The BOC Group plc Dispositif de combustion
US20020090587A1 (en) * 2001-01-05 2002-07-11 Pribish Vincent R. Burner for high-temperature combustion

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Publication number Priority date Publication date Assignee Title
US4362274A (en) * 1980-06-27 1982-12-07 Coen Company, Inc. Dual fuel atomizer
IT1263683B (it) * 1992-08-21 1996-08-27 Westinghouse Electric Corp Complesso di ugello per combustibile per una turbina a gas
DE10158805A1 (de) * 2001-11-30 2003-06-18 Siemens Ag Schiffsantrieb
US7082765B2 (en) * 2004-09-01 2006-08-01 General Electric Company Methods and apparatus for reducing gas turbine engine emissions

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0375311A1 (fr) * 1988-12-22 1990-06-27 General Electric Company Couvercle incorporé de buse à carburant pour chambre de combustion d'une turbine à gaz
EP0473906A1 (fr) * 1990-08-01 1992-03-11 Corning Incorporated Ensemble de brûleur d'oxygène-combustible et le régime
EP0718554A2 (fr) * 1994-12-20 1996-06-26 The BOC Group plc Dispositif de combustion
US20020090587A1 (en) * 2001-01-05 2002-07-11 Pribish Vincent R. Burner for high-temperature combustion

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2520857A1 (fr) * 2011-05-05 2012-11-07 General Electric Company Buse de chambre de combustion et procédé pour fournir du carburant à une chambre de combustion
EP2653698A1 (fr) * 2012-04-19 2013-10-23 Linde Aktiengesellschaft Procédé de fonctionnement d'une unité de turbine à gaz

Also Published As

Publication number Publication date
EP2162678A1 (fr) 2010-03-17
CN101772674A (zh) 2010-07-07
WO2009007293A1 (fr) 2009-01-15
US20100186417A1 (en) 2010-07-29

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